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EP2366099B1 - Capteur d état de santé structurelle stratifié hibride, résistant et frangible - Google Patents

Capteur d état de santé structurelle stratifié hibride, résistant et frangible Download PDF

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Publication number
EP2366099B1
EP2366099B1 EP09792166.2A EP09792166A EP2366099B1 EP 2366099 B1 EP2366099 B1 EP 2366099B1 EP 09792166 A EP09792166 A EP 09792166A EP 2366099 B1 EP2366099 B1 EP 2366099B1
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EP
European Patent Office
Prior art keywords
sense loop
material layer
conductive
corrosion
conductive material
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EP09792166.2A
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German (de)
English (en)
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EP2366099A1 (fr
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Gregory L. Sheffield
Matthew K. Fay
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Boeing Co
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Boeing Co
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
    • G01N17/04—Corrosion probes

Definitions

  • This disclosure relates to structural testing. Particularly, this disclosure relates to techniques for monitoring the integrity of structural elements over time in service.
  • US 2007/0173048A1 discloses an apparatus and a corresponding method for sensing structural integrity, wherein a resistance sensor and a corrosion sensor are incorporated in a foil sensor bonded to an insulating substrate.
  • Visual inspection of structural members often requires some degree of disassembly of the structure. This adds greatly to the overall testing cost. For example, visual inspection for aircraft structures requires substantial disassembly of structure and removal of installed equipment in order to provide the access needed to view the areas of interest at a distance adequate to detect corrosion visually.
  • X-Ray testing under the broader heading of radiographic testing, requires specialized facilities and government licenses.
  • the technique employs the ability of short wavelength electromagnetic radiation to penetrate various materials. Either an X-ray machine or a radioactive source can be used as a source of photons. Because the amount of radiation emerging from the opposite side of an examined material can be detected and measured, variations in the intensity of radiation are used to determine thickness or composition of material and reveal any and reveal any defects. Due to safety issues, X-ray testing also typically requires a complete work stoppage on all other tasks while the testing is being performed.
  • Dye penetrant testing is also time consuming and messy.
  • Dye penetrant inspection is used to reveal surface breaking flaws through the bleedout of a colored or fluorescent dye from the flaw. The technique is based on the ability of a liquid to be drawn into a surface breaking flaw by capillary action. After a period of time, excess surface penetrant is removed and a developer is applied. This acts as a blotter. It draws the penetrant from the flaw to reveal its presence. The consituent penetrant and developer may and their by-products may be identified as hazardous (HAZMAT), requiring costly disposal means.
  • HZMAT hazardous
  • inspection methods using the application of electrical fields are exceptionally time consuming and difficult to read reliably in this type of application and may require alterations to structure.
  • eddy current testing for example, a circular coil carrying an AC current is placed in close proximity to an electrically conductive specimen to be tested. The alternating current in the coil yields a changing magnetic field, which interacts with the test object and induces eddy currents in it. Variations in the phase and magnitude of these eddy currents can be monitored using a second coil, or by measuring changes to the current flowing in the primary coil.
  • the presence of any flaws or variations in the electrical conductivity or magnetic permeability of the test object will cause a change in eddy current flow and a corresponding change in the phase and amplitude of the measured current.
  • the technique is generally limited to detecting surface breaks or near surface cracking and variations in material composition.
  • a hybrid sensor device for monitoring and testing for both possible fractures and corrosion in structural elements is disclosed.
  • a frangible material layer including a thin breakable conductor sense loop and a resilient material layer including a conductive corrosion sense loop bonded on top of the frangible layer form an assembly which is bonded to a structural element to be tested. Portions of the conductive corrosion sense loop are exposed through weep holes in the resilient material layer.
  • a fracture in the bonded structural element induces a disruption in both the frangible membrane and the thin breakable conductor sense loop and corrosion of the conductive corrosion sense loop changes its electrical properties. Measured electrical property changes of the disrupted conductor sense loop and/or the conductive corrosion sense loop reveal possible damage.
  • Both sensor layers may utilize a single shared wireless communications tag to couple to an electrical measuring device.
  • a typical sensor embodiment of the invention comprises an apparatus for sensing structural integrity, including a frangible non-conductive material layer, a resilient non-conductive material layer disposed on top of the frangible non-conductive material layer, a breakable conductor sense loop within the frangible non-conductive material layer, and a conductive corrosion sense loop within the resilient non-conductive material layer and having a portion exposed through at least one weep hole in the resilient non-conductive material layer.
  • the frangible non-conductive material is disposed adjacent to a structure surface such that the breakable conductor sense loop can be disrupted by a fracture in the structure surface and the exposed portion of the conductive corrosion sense loop can corrode to induce a change in an electrical property of the conductive corrosion sense loop.
  • the breakable conductor sense loop and the structure surface may comprise a common material.
  • the frangible non-conductive material layer is bonded to the structure surface.
  • a disruption of the breakable conductor sense loop from the fracture in the structure surface and the change in the electrical property of the conductive corrosion sense loop from may be sensed through an electrical measuring device coupled to both the breakable conductor sense loop and the conductive corrosion sense loop.
  • the sensor further comprises a wireless communications tag for coupling the electrical measuring device to both the breakable conductor sense loop and the conductive corrosion sense loop.
  • a wired connecting device may be used for coupling the electrical measuring device to both the breakable conductor sense loop and the conductive corrosion sense loop.
  • a second structure surface may be disposed above the resilient non-conductive material layer, e.g. as used in a gasket configuration.
  • the resilient non-conductive material layer may comprise one or more sealing ribs against the second structure surface.
  • construction of the frangible non-conductive material layer may comprise two layers sandwiching the breakable conductor sense loop.
  • construction of the resilient non-conductive material layer may comprise two layers sandwiching the conductive corrosion sense loop.
  • a typical method for sensing structural integrity comprises the steps of disposing a frangible non-conductive material having a breakable conductor sense loop within the frangible non-conductive material adjacent to a structure surface, disposing a resilient non-conductive material layer on top of the frangible non-conductive material layer having a conductive corrosion sense loop within the resilient non-conductive material layer and having a portion of the conductive corrosion sense loop exposed through at least one weep hole in the resilient non-conductive material layer, sensing a disruption in the breakable conductor sense loop from a fracture in the structure surface, and sensing a change in an electrical property of the conductive corrosion sense loop from corrosion in the exposed portion of the conductive corrosion sense loop.
  • Method embodiments of the invention may be further modified consistent with the apparatus embodiments described herein.
  • embodiments of the disclosure are directed to a technique for detecting both a discontinuity caused by a defect (e.g., a fracture) in a structural element as well as possible corrosion in the structural element.
  • This hybrid sensor combines the features of two previously described sensors (a fracture detecting sensor described in United States Patent Application No. 11/941,307, by Fay et al. filed November 16, 2007 , and a corrosion detecting sensor described in United States Patent Application No. 11/941,367, by Fay et al. filed November 16, 2007 ) into one integrated sensor with the combined capabilities of both corrosion and crack detection.
  • the dual layer membrane sensor effectively becomes a part of the structure on which it is installed.
  • the sensor can provide the user with corrosion and/or damage status in a quick and reliable way.
  • the sensor does not require special facilities, tools, training or equipment to operate.
  • the sensor comprises at least two distinct material layers including a frangible non-conductive layer with an embedded breakable conductor sense loop and a resilient non-conductive layer with an embedded conductive corrosion sense loop.
  • This hybrid sensor configuration may be constructed by bonding a resilient gasket corrosion sensor section directly to a frangible fracture sensor section. At installation, the fracture sensor section can be bonded directly to the structure of interest.
  • the frangible non-conductive layer is bonded to a structural element such that a fracture in the structural element produces a corresponding fracture in the membrane and a break in the breakable conductor sense loop.
  • the structural element may be any material, e.g. metallic or composite.
  • the resilient non-conductive layer is disposed on a top surface of the frangible non-conductive layer and includes at least one weep hole to expose a portion of the conductive corrosion sense loop. Possible corrosion of the nearby structure is indicated by corrosion of the conductive corrosion sense loop which causes a change in its electrical properties.
  • Disruption of the breakable conductor sense loop and corrosion of the conductive corrosion sense loop are both detectable with an electrical measuring device coupled to the separate loops. Alternately, separate electrical measuring devices may also be used. Connection to the sense loops can be made through an ordinary electrical connector or a wireless communication tag. In the described hybrid sensor, both sensor layers may utilize a single shared wireless communications tag to couple to an electrical measuring device.
  • a wireless reader measuring device may be used to provide RF signals for energizing circuitry, controlling functionality, and receiving data.
  • the sensor can provide detection capability without the need to remove the installed unit from of service for extended lengths of time, in the absence of corrosion or damage severe enough to require repair. In contrast, conventional techniques for inspecting structures are all exceptionally time consuming and expensive.
  • the bonded frangible sensor layer and resilient corrosion sensor layer together can detect hidden fractures, other structural damage and possible corrosion without any component or structural disassembly.
  • embodiments of the disclosure can mitigate any required disassembly of components or structures as would otherwise be required to perform routine visual inspections. Further, embodiments of the disclosure do not require special facilities, training or government licenses. Embodiments of the disclosure can also provide a quicker process for determining whether structural defects are present without interrupting other work in progress.
  • a hybrid sensor in accordance with the disclosure can lower the total cost of ownership (e.g., of an aircraft) based on the labor it can save and the additional equipment availability it can provide. Operators will not have to take equipment out of service, provided that there are no incidents of damage that need to be repaired. In contrast, conventional methods require copious labor and extended periods out of service to accomplish - even if no repairs are required. Conventional methods also enhance the risk of maintenance induced damage during the disassembly required for access.
  • FIG. 1A illustrates a cross section of an exemplary hybrid resilient and frangible layered structural health sensor 100.
  • the sensor 100 comprises a frangible material layer 104 formed into a thin flat structure that is disposed adjacent to the surface of the structure 102. Typically the frangible material layer 104 is bonded to the structure 102. At least one breakable conductor sense loop 106 is embedded within the frangible material layer 104.
  • the frangible material layer 104 must be non-conductive so as not to short the breakable conductor sense loop 106 which is employed to detect a fracture or other structural failure in the surface of the structure 102.
  • a separate resilient material layer 108 is disposed on top of the frangible material layer 104.
  • the resilient material layer 108 has at least one conductive corrosion sense loop 110 embedded within it.
  • the resilient material layer 108 includes one or more weep holes 112 which penetrate to expose a portion of the conductive corrosion sense loop 110.
  • the resilient material layer 108 is also non-conductive to avoid shorting the conductive corrosion sense loop 110.
  • the sensor 100 may be employed in a gasket configuration.
  • the surface of a second structure 114 is disposed above the resilient non-conductive material layer 108.
  • the resilient non-conductive material layer 108 may include one or more sealing ribs 116 against the surface of the second structure 114.
  • FIG. 1B illustrates a cross section of an exemplary hybrid resilient and frangible layered structural health sensor indicating a structural failure.
  • a fracture 118 appearing in the surface of the structure 102 induces a break 120 in the frangible material layer 104 which in turn carries through to cause a break 122 in the breakable conductor sense loop 104.
  • Possible corrosion in the nearby structures 102, 114 is detected by the resilient non-conductive material layer 108 of the sensor 100.
  • the detected disruption in the breakable conductor sense loop 104 is a break (which may be a complete break or a partial break through the breakable conductor sense loop 104).
  • any variation in the measured electrical properties of the breakable conductor sense loop 104 may also be employed to detect the disruption and indicate a fracture or other problem in the underlying structure.
  • Possible corrosion in the nearby structures 102, 114 is indicated by corrosion of the conductive corrosion sense loop 110 in portion exposed by the one or more weep holes 112. Any corrosion 124 that develops on the conductive corrosion sense loop 110 in the one or more weep holes 112 in the resilient non-conductive material layer 108 will affect the electrical properties of the conductive corrosion sense loop 110.
  • the material of the conductive corrosion sense loop 110 may be selected to be susceptible to corrosion so that any moisture that comes in contact with the area will enter the weep hole 112 and cause at least a partial reduction of the exposed portion of the conductive corrosion sense loop 110. This will result in an increase in the effective resistance of the conductor as the cross sectional area of the conductor is reduced by the corrosion.
  • the weep hole 112 allows the conductive corrosion sense loop 110 to provide an early warning of possible corrosion to the structural elements due to the presence of moisture. Excessive corrosion that may develop in the weep holes 112 in the resilient material layer 108 may also cause a disruption in the conductive corrosion sense loop 110 as well. It should be noted that design of the conductive corrosion sense loop 110 may be optimized such that the portions of the conductive corrosion sense loop 110 may be treated differently or comprise a different material than the unexposed portions of the conductive corrosion sense loop 110 to enhance the corrosion sensitivity in this area.
  • both the breakable conductor sense loop 106 and the conductive corrosion sense loop 110 are connected to a connecting device which is coupled to a measuring device that detects the fracture or corrosion as illustrated in example hybrid layered fracture and corrosion sensor installation described in the next section.
  • the frangible material layer may be constructed from two layers of thin plastic frangible film which contains the one or more fine wire sense loops sandwiched between.
  • the frangible frangible material layer may be curable such that it is flexible prior to installation, but becomes rigid and brittle when fully cured.
  • damage such as a crack occurs on the underlying structure
  • the frangible membrane cracks as well, breaking the wire sense loop at the location of the damage.
  • the frangible material layer is a non-conductive material that may be self-adhesive at installation and effectively seals and protects the underlying structure from corrosion.
  • the resilient material layer may also be constructed from two layers of thin plastic which contains one or more wire sense loops.
  • the resilient material layer may also be curable, but it cures to a resilent material.
  • the resilient material layer is also non-conductive and may be self-adhesive to the top of the frangible material layer. As described above, one or more weep holes in the top of the resilient material layer permit the conductive corrosion sense loop to indicate possible corrosion.
  • the sensor may be installed at structural locations where cracks and/or corrosion are a concern, such as fastener holes and cutouts in pressurized structure.
  • an operator uses a reader device to energize and read the sensor.
  • Either a wireless reader device or another external device may be used to compare the readings of a sense loop to those of a reference value measured at each specific installation to determine if possible corrosion or damage is present.
  • the reference value can be determined when the sensor is designed for a specific application and manufactured.
  • the reference value for the specific application can either exist in written form for manual measurement and analysis or be loaded into the wireless reader for automatic analysis.
  • the frangible and resilient layer share some common properties but also have distinct characteristics.
  • the frangible material layer is non-porous and frangible (brittle) after installation.
  • Materials for the frangible material layer may have characteristics similar to paint coatings in appearance.
  • the objective is that the composition of the frangible material layer should match the structure material it is bonded to such that if a crack occurs in the structural element, the frangible material layer cracks as well, breaking the conductor which forms the sense loop.
  • the resilient material layer should be flexible after installation. Both material layers may be either a pre-formed device or fabricated on site. Both the frangible and resilient material layers should be an effective electrical insulator and flexible enough prior to installation to permit ease of installation.
  • Both material layers should have good shelf-life quality to permit stocking of spares. Both layers must be non-corrosive, particularly to the conductive corrosion sense loop. The proper layer and sense loop materials and sizes and electrical measurement characteristics can be selected for a specific installation to maximize sensor performance.
  • the different materials for the frangible membrane layer may comprise, but are not limited to, polycarbonate, urethane, polyurethane, enamel, polyester, acrylic, epoxy, and a wide variety of plastics and other similar materials.
  • the materials for the resilient gasket layer may comprise, but are not limited to, silicone, rubber, nitrile, Buna-N, neoprene, Teflon, and other similar materials.
  • the sense loops may be custom tailored to the specific application.
  • the breakable conductor sense loop it can typically be constructed from the same material (e.g., base metal and alloy) as the structural element at the installed interface.
  • the configuration and size of the sense loop should be appropriate to ensure the conductor breaks when and if the membrane breaks.
  • the conductive corrosion sense loop need not be breakable. Materials for the sense loop include, but are not limited to aluminum, steel, copper, magnesium, titanium, and other similar materials.
  • a membrane sensor device may also be implemented in a gasket configuration as described in the next section.
  • FIGS. 2A to 2C illustrate a top view and two cross sections, respectively of an exemplary hybrid resilient and frangible layered structural health sensor 200.
  • FIG. 2B illustrates cross section A-A
  • FIG. 2C illustrates cross section B-B of the exemplary hybrid resilient and frangible layered structural health sensor 200 shown in FIG. 2A .
  • the sensor 200 comprises a frangible and a resilient material layer 204A, 204B formed into a thin flat structure that is disposed adjacent between the surfaces of two structures 202A, 202B as shown in the cross sections of FIGS. 2B and 2C .
  • the frangible material layer 204A is disposed on the surface of a first structure 202A.
  • frangible material layer 204A must be non-conductive so as not to short the breakable conductor sense loops 206A, 206B, 206C employed to detect a fracture or other structural failure in the surface either of the structures 202A, 202B in the manner previously described regarding FIGS. 1A and 1B .
  • the resilient material layer 204B is disposed on top of the frangible material layer 204A.
  • the resilient material layer 204B includes multiple weep holes 230A-230R which penetrate the layer 204B to expose distinct portions of a conductive corrosion sense loop 208.
  • the conductive corrosion sense loop 208 can be used to provide early detection of corrosion as previously described regarding FIGS. 1A and 1B .
  • the gasket configuration of the sensor 200 can also include one or more ribs 210A, 210B built into the top surface of the resilient material layer 204B.
  • the ribs 210A, 210B are designed to provide a seal against the adjacent surface of the structure 202B.
  • the conductive corrosion sense loop 208 material may be selected to be susceptible to corrosion so that any moisture that comes in contact with the area will enter one or more of the weep holes 230A-230R and cause at least a partial erosion of the conductor. This will result in an increase in the effective resistance of the conductor as the cross sectional area of the conductor is reduced by the corrosion.
  • the weep holes 230A-230R allow the conductive corrosion sense loop 208 to provide an early warning of possible corrosion to the structural element due to the presence of moisture.
  • the gasket configuration is particularly well suited for early corrosion detection because the top surface of resilient material layer 204B is intended to remain sealed from the environment (with or without the sealing ribs 210A, 210B). Thus, a visual inspection of the area would not reveal any moisture present in the weep holes 230A-230R.
  • both the conductive corrosion sense loop 208 and the three breakable conductor sense loops 206A, 206B, 206C are connected to a connecting device which can then be coupled to a measuring circuit that detects the fracture or corrosion.
  • Communication with the sensor 200 may be accomplished using any known technique.
  • the two layers 204A, 204B are sandwiched between the surfaces of two structures 202A, 202B as described in FIGS. 2B and 2C .
  • the structures 202A, 202B may be a joint between two components in an aircraft.
  • a series of bolts 224A-224R are disposed around the interface between the structures 202A, 202B.
  • breakable conductor sense loops 206A, 206B, 206C are embedded within the frangible material layer 204A as previously described and is routed around the interface as well.
  • the breakable conductor sense loops 206A, 206B, 206C are laid perpendicular to where any structural failures are likely to appear.
  • Ribs 210A, 210B are also laid out around the perimeter of both the inner and outer edges of the sensor 200 on the top side of the resilient material layer 204B as previously described in FIGS. 2B and 2C to seal the layer surface and the structure 202B surface from moisture.
  • the breakable conductor sense loops 206A, 206B, 206C and the conductive corrosion sense loop 208 of the gasket sensor 200 are coupled to a connecting device 232 which is used to connect to a electrical measuring device that measures changes in the electrical properties of the loops 206A, 206B, 206C, 208 (e.g., resistance increase indicating corrosion or an open circuit indicating a fracture).
  • the electrical measuring device can be any known device capable of measuring the appropriate electrical properties of the loops 206A, 206B, 206C, 208.
  • the connecting device 232 may comprise an electrical connector.
  • the connecting device 232 may also comprise a wireless communication tag as described in the next section which affords many advantages beyond a simple electrical connector. The wireless communication tag incorporates some of the reader device with the tag.
  • FIG. 3A illustrates a wireless communication tag 300 that may be coupled to a structural sensor 310.
  • the example wireless communications tag 300 comprises one or more RF receivers 302.
  • the one or more receivers 302 are coupled to a series of rectifier circuits 304 and a demodulator 306.
  • the RF receivers should be designed with one or more resonant frequencies to maximize the excitation of the receiver rectifier circuits and demodulators.
  • Each RF receiver rectifier circuit 304 may be associated with a specific series and/or parallel resonant frequency to maximize signal voltage 308 generated to power necessary sections of the tag and sensor 310 (i.e., the sense loop) during different modes of operation.
  • Voltage 308 from the rectifiers 304 is supplied to the sensor 310 that yields measurands 318 to the measurement logic circuit 312.
  • the clock 302 and control 330 signals from the demodulator 306 are used to control the measurement logic 312 to convert measurands 318 into data 334 transferred to memory 314.
  • the demodulator 306 clock 332 is used to generate the clock signal from the measurement logic 312 for clocking data into memory 314.
  • the clock and control signals from the demodulator 322 are used to control the logic controller 326 to read and write data into memory 314.
  • the RF receiver 302 may comprise one or more series and/or parallel resonant frequencies for the receiver demodulator 306 to properly control and synchronize the measurement logic 312 and targeted locations of the memory 314.
  • the RF receiver 302 antenna 316 may support a series and parallel resonant frequencies by using a distributed capacitance, inductance, and resistance as known in the art.
  • the RF receiver 302 may be designed to operate using OFDM, CDMA or any other multi-carrier resonant frequencies across the frequency spectrum known in the art.
  • the RF receiver 302 should be designed with safeguard features to ensure inappropriate operations do not occur based on safety requirements.
  • FIG. 3B illustrates an example safeguard feature for a receiver 302 (such as the RF receiver 302 of FIG. 3A ) in a wireless communication tag 300.
  • Sets of unique resonant frequency (or frequency pattern) inputs 348 (1 - n 1 ), 350 (1 - n 2 ), 352 (1 - n 3 ) are used to respectively direct the power, clock and control of the device.
  • the sets of power resonant frequency inputs 348 direct the rectifiers (e.g., rectifiers 304 of FIG. 3A ), while the sets of clock and control resonant frequency inputs 350, 352 direct the demodulator (e.g., demodulator 306 of FIG. 3A ) of the device.
  • the rectifiers e.g., rectifiers 304 of FIG. 3A
  • the sets of clock and control resonant frequency inputs 350, 352 direct the demodulator (e.g., demodulator 306 of FIG. 3A ) of the device.
  • Embodiments of the disclosure may further implement a safeguard feature for preventing inadvertent activities of the overall device may use a set of safeguard resonant frequency inputs 354 (1 - n 4 ) per device.
  • the safeguard resonant frequency inputs 354 may be either unique resonant frequency patterns or a subset of the frequencies used from the power, clock, and/or control resonant frequencies inputs 348, 350, 352.
  • the activity logic 340 operates to enable the power, clock and control gates 342, 344, 346, respectively, only when the set of safeguard resonant frequency inputs 354 (e.g., specific frequencies with corresponding amplitudes) meet the required safeguard conditions of the activity logic circuit 340.
  • the activity logic 340 may require specific timing or sequencing of the receiving sets of frequency inputs 348, 350, 352, 354.
  • the safeguard conditions may be statically part of the activity logic circuit 340 or implemented in a way that allows for reconfiguration, e.g., through a programmable element.
  • the RF transponder 318 should be designed with one or more resonant frequencies to maximize the excitation of the one or more transponder rectifier circuits 320, demodulators 322, and modulators 324.
  • the RF transponder 318 may operate using RFID technology known in the art.
  • Each RF transponder rectifier circuit 320 should be associated with a specific series and/or parallel resonant frequency to maximize signal voltage generated to power necessary sections of the tag during different modes of operation.
  • the RF transponder 318 may be designed with one or more series and/or parallel resonant frequencies for the transponder demodulator 322 to properly control and sync the transponder control logic 326 and targeted locations of the memory 314.
  • the RF Transponder 318 should be designed with one or more series and/or parallel resonant frequencies for the transponder modulator 324 to properly generate transmission signals externally to a reader (not shown) through the antenna 328.
  • the RF transponder 318 should include all or a subset of the frequency bands supporting RFID as known in the art.
  • the RF Transponder should be designed with safeguard features to ensure inappropriate operations do not occur based on safety requirements.
  • the measurement logic 312 may support the input measurands 318 from the sensor 310 (sense loop), convert the measurand 318 values into a digital format, and write the values into targeted portions of the memory 314 on a data channel 334.
  • the measurement logic 312 may support serial or parallel control 330 and clock 332 signals.
  • the memory 314 may support, at minimum, non-volatile reference information (e.g., identification, encryption key) and non-volatile or volatile value fields (e.g., measurements). Further, the memory 314 may also support serial or parallel reads and writes. All demodulators 306, 322 may provide serial and/or parallel control and clock signals.
  • the logic controller 326 may provide read capabilities of the targeted memory 314 region and simultaneously input into the modulator 324.
  • the wireless communication tag may be designed to operate with a range sensors such as that previously described including both fracture and/or corrosion sensing. Additionally, the wireless communication tag may be designed to operate with any other sensor that may be installed to monitor a structure.
  • multiple structural sensors e.g., hybrid fracture and corrosion sensors
  • each have a wireless communication tag are installed in an aircraft structure and employed under an overall testing plan.
  • the sensors are first installed at their various location during the aircraft build. A first reading is performed for all the sensors to validate their functioning and to provide identification and sensor results with a reader device. Following this, the aircraft build is completed and the sensors are then revalidated for functionality. (This sensor installation may occur during the original aircraft build or a retrofit during aircraft maintenance.) The identification and location of the various sensors are recorded. The sensors are next read at a scheduled inspection and any indicated problems repaired. An example reading process is described hereafter.
  • a wireless reader device is employed to read identification numbers of sensors by transmitting a "ping" to a localized area of the aircraft structure where one or more sensors are installed. Any sensors in the area respond with their identification numbers. The indentification numbers are then cross-referenced to aircraft records to determine the sensor locations. The reader then interrogates all the sensors by transmitting another "ping" to energize sense element circuitry of the sensors. Each sensor tag is powered by the voltage induced in it by the readers transmitted power. The wireless communication tag then verifies that the induced power is within system specifications. An error message is returned to the reader if this fails. If successful, the sense portion of the tag then energizes the conductor sense loop. The sense portion of the tag then reads electrical characteristics of the energized sense loop.
  • the tag then transmits sense element readings to the reader for analysis.
  • the reader then receives the transmitted tag data and compares the values to reference standards for the respective sensors. Finally, the reader displays the inspection results for each sensor. The next regular inspection is scheduled if the result is successful or a repair is scheduled if a failure is indicated.
  • FIG. 4 is a flowchart of a method 400 of sensing a structural integrity.
  • the method 400 begins with a first operation 402 of disposing a frangible non-conductive material having a breakable conductor sense loop within the frangible non-conductive material adjacent to a structure surface.
  • a resilient non-conductive material layer is disposed on top of the frangible non-conductive material layer having a conductive corrosion sense loop within the resilient non-conductive material layer and having a portion of the conductive corrosion sense loop exposed through at least one weep hole in the resilient non-conductive material layer.
  • a disruption in the breakable conductor sense loop is sensed from a fracture in the structure surface.
  • a change in an electrical property of the conductive corrosion sense loop from corrosion in the exposed portion of the conductive corrosion sense loop is sensed.
  • This method 400 for sensing structural integrity may be modified consistent with any of the devices or other methods described herein.
  • operation 404 is performed first in a manufacturing process bonding the resilient non-conductive material layer to the frangible non-conductive material layer to produce the hybrid sensor and operation 402 is performed later when the hybrid sensor is installed on the structure.
  • these two operations may be performed in the opposite order.
  • the hybrid sensor may be assembled as it is installed on the structure with the frangible non-conductive material layer first bonded to the structure in operation 402 and the resilient non-conductive material layer bonded on top of the frangible non-conductive material layer thereafter in operation 404.
  • FIG. 5 is flowchart of a sub-method 500 of operations 406 and 408 for sensing using the sense loops.
  • Sub-method 500 of sensing with the sense loops begins with the operation 502 of connecting the breakable conductor sense loop and the conductive corrosion sense loop to a wireless communications tag.
  • a wireless link is formed between the wireless communications tag and an electrical measuring device.
  • a disruption in the breakable conductor sense loop is detected with the electrical measuring device.
  • a change in an electrical property (e.g., a resistance change) of the conductive corrosion sense loop is measured with the electrical measuring device.
  • This method 500 for sensing with the two sense loops may be modified consistent with any of the devices or other methods described herein.

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  • Investigating Or Analyzing Materials By The Use Of Electric Means (AREA)

Claims (14)

  1. Appareil destiné à détecter une intégrité structurale dans une surface adjacente (102 ; 202A), comprenant :
    une couche de matériau non conducteur fragile (104 ; 204A) ;
    une couche de matériau non conducteur résilient (108 ; 204B) disposée au-dessus de la couche de matériau non conducteur fragile (104 ; 204A) ;
    une boucle de détection à conducteur cassant (106 ; 206A-C) à l'intérieur de la couche de matériau non conducteur fragile (104 ; 204A) qui se casse quand il y a une fracture dans la surface de structure adjacente ; et
    une boucle de détection de corrosion conductrice (110 ; 208) à l'intérieur de la couche de matériau non conducteur résilient (108 ; 204B) et ayant une partie exposée à travers au moins un trou d'évacuation d'eau (112 ; 230A-R) dans la couche de matériau non conducteur résilient (108) pour induire un changement dans une propriété électrique de la boucle de détection de corrosion conductrice (110 ; 208) quand :
    la partie exposée de la boucle de détection de corrosion conductrice (110 ; 208) se corrode.
  2. Appareil de la revendication 1, comprenant en outre un dispositif de mesure électrique (300) couplé à la fois à la boucle de détection à conducteur cassant (106 ; 206A-C) et la boucle de détection de corrosion conductrice (110 ; 208), une interruption de la boucle de détection à conducteur cassant et le changement dans la propriété électrique de la boucle de détection de corrosion conductrice étant détectés par ledit dispositif de mesure électrique (300).
  3. Appareil de la revendication 2, comprenant en outre une étiquette de communication sans fil (300) destinée à coupler le dispositif de mesure électrique à la fois à la boucle de détection à conducteur cassant et la boucle de détection de corrosion conductrice.
  4. Appareil de la revendication 2, comprenant en outre un dispositif de connexion filaire destiné à coupler le dispositif de mesure électrique à la fois à la boucle de détection à conducteur cassant et la boucle de détection de corrosion conductrice.
  5. Appareil de la revendication 1, dans lequel la boucle de détection à conducteur cassant (106 ; 206A-C) et la surface de structure comprennent un matériau commun.
  6. Appareil de la revendication 1, dans lequel la couche de matériau non conducteur fragile (104 ; 204A) est liée à la surface de structure.
  7. Appareil de la revendication 1, dans lequel une deuxième surface de structure est disposée au-dessus de la couche de matériau non conducteur résilient (108 ; 204B).
  8. Appareil de la revendication 7, dans lequel la couche de matériau non conducteur résilient (108 ; 204B) comprend une ou plusieurs nervures d'étanchéité contre la deuxième surface de structure.
  9. Appareil de la revendication 1, dans lequel la couche de matériau non conducteur fragile (104 ; 204A) comprend deux couches entourant la boucle de détection à conducteur cassant.
  10. Appareil de la revendication 1, dans lequel la couche de matériau non conducteur résilient (108 ; 204B) comprend deux couches entourant la boucle de corrosion conductrice.
  11. Procédé de détection d'une intégrité structurale, comprenant les étapes consistant à :
    disposer un matériau non conducteur fragile ayant une boucle de détection à conducteur cassant à l'intérieur du matériau non conducteur fragile au voisinage d'une surface de structure ;
    disposer une couche de matériau non conducteur résilient au-dessus de la couche de matériau non conducteur fragile ayant une boucle de détection de corrosion conductrice à l'intérieur de la couche de matériau non conducteur résilient et ayant une partie de la boucle de détection de corrosion conductrice exposée à travers au moins un trou d'évacuation d'eau dans la couche de matériau non conducteur résilient ;
    détecter une interruption dans la boucle de détection à conducteur cassant provenant d'une fracture dans la surface de structure ; et
    détecter un changement dans une propriété électrique de la boucle de détection de corrosion conductrice provenant de la corrosion dans la partie exposée de la boucle de détection de corrosion conductrice.
  12. Procédé de la revendication 11, dans lequel une interruption de la boucle de détection à conducteur cassant provenant de la fracture dans la surface de structure et le changement dans la propriété électrique de la boucle de détection de corrosion conductrice sont détectés par un dispositif de mesure électrique couplé à la fois à la boucle de détection à conducteur cassant et la boucle de détection de corrosion conductrice.
  13. Procédé de la revendication 12, dans lequel une étiquette de communication sans fil couple le dispositif de mesure électrique à la fois à la boucle de détection à conducteur cassant et la boucle de détection de corrosion conductrice.
  14. Procédé de la revendication 12, dans lequel un dispositif de connexion filaire couple le dispositif de mesure électrique à la fois à la boucle de détection à conducteur cassant et la boucle de détection de corrosion conductrice.
EP09792166.2A 2008-09-02 2009-09-02 Capteur d état de santé structurelle stratifié hibride, résistant et frangible Active EP2366099B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/202,883 US8138773B2 (en) 2008-09-02 2008-09-02 Hybrid resilient and frangible layered structural health sensor
PCT/US2009/055720 WO2010028035A1 (fr) 2008-09-02 2009-09-02 Capteur d’état de santé structural hybride, stratifié, résilient et cassant

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EP2366099B1 true EP2366099B1 (fr) 2017-12-27

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CA2726723A1 (fr) 2010-03-11
CN102112862B (zh) 2014-06-25
US20100052704A1 (en) 2010-03-04
WO2010028035A1 (fr) 2010-03-11
CA2726723C (fr) 2013-12-31
JP2012501461A (ja) 2012-01-19
US8138773B2 (en) 2012-03-20
JP5450629B2 (ja) 2014-03-26
CN102112862A (zh) 2011-06-29
EP2366099A1 (fr) 2011-09-21

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